EP2226509A3 - Turbo compressor or pump with fluid injection to influence the boundary layer - Google Patents

Turbo compressor or pump with fluid injection to influence the boundary layer Download PDF

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Publication number
EP2226509A3
EP2226509A3 EP10006367A EP10006367A EP2226509A3 EP 2226509 A3 EP2226509 A3 EP 2226509A3 EP 10006367 A EP10006367 A EP 10006367A EP 10006367 A EP10006367 A EP 10006367A EP 2226509 A3 EP2226509 A3 EP 2226509A3
Authority
EP
European Patent Office
Prior art keywords
blade
rotor
stator
edge
trailing edge
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP10006367A
Other languages
German (de)
French (fr)
Other versions
EP2226509B1 (en
EP2226509A2 (en
Inventor
Volker Dr. Gümmer
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Rolls Royce Deutschland Ltd and Co KG
Original Assignee
Rolls Royce Deutschland Ltd and Co KG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Rolls Royce Deutschland Ltd and Co KG filed Critical Rolls Royce Deutschland Ltd and Co KG
Publication of EP2226509A2 publication Critical patent/EP2226509A2/en
Publication of EP2226509A3 publication Critical patent/EP2226509A3/en
Application granted granted Critical
Publication of EP2226509B1 publication Critical patent/EP2226509B1/en
Expired - Fee Related legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/20—Specially-shaped blade tips to seal space between tips and stator
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/145—Means for influencing boundary layers or secondary circulations
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
    • F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
    • F04D29/684—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps by fluid injection
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/01—Purpose of the control system
    • F05D2270/10—Purpose of the control system to cope with, or avoid, compressor flow instabilities
    • F05D2270/101—Compressor surge or stall
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/01—Purpose of the control system
    • F05D2270/17—Purpose of the control system to control boundary layer
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Abstract

Die Erfindung bezieht sich auf eine Strömungsmaschine mit zumindest einem Rotor 6, der mehrere an einer rotierenden Welle befestigte Rotorschaufeln 8 umfasst, sowie mit einem einen Ringkanal bildenden Gehäuse 1, welches unter Durchströmung des Rotors 6 und/oder eins Stators 9 von einem Fluid durchströmt wird,
wobei Mittel zur Zufuhr von Fluid an mindestens einer Schaufel 8 einer Schaufelreihe des Rotors 6 und /oder des Stators 9 an aerodynamisch kritischen Orten auf hinterkanten- und randnahen Oberflächen (HRO) vorgesehen sind,
wobei zur gezielten Beeinflussung der dreidimensionalen Strömung im Bereich der Schaufelenden Mittel zur Zufuhr von Fluid an hinterkanten- und randnahen Oberflächen (HRO) an Oberflächen der Naben- oder Gehäusekontur des Ringkanals 10 im Bereich einer festen Verbindung zur Schaufel zwischen die Hinterkantenebene (HK) der Schaufel und einer 25% der meridionalen Schaufelsehnenlänge Cm stromauf der Vorderkante (VK) befindlichen Ebene an einem Rotor 8 oder Stator 9 ausgebildet sind.

Figure imgaf001
The invention relates to a turbomachine with at least one rotor 6, which comprises a plurality of rotor blades mounted on a rotating shaft 8, as well as with an annular channel forming housing 1, which is flowed through by flow of the rotor 6 and / or a stator 9 of a fluid .
wherein means for supplying fluid to at least one blade 8 of a blade row of the rotor 6 and / or the stator 9 are provided at aerodynamically critical locations on trailing edge and near-edge surfaces (HRO),
wherein for the targeted influencing of the three-dimensional flow in the region of the blade ends means for supplying fluid to trailing edge and near-edge surfaces (HRO) on surfaces of the hub or housing contour of the annular channel 10 in the region of a fixed connection to the blade between the trailing edge plane (HK) of the blade and a 25% of the meridional blade chord length Cm upstream of the leading edge (VK) plane is formed on a rotor 8 or stator 9.
Figure imgaf001
EP10006367A 2003-11-26 2004-10-12 Turbo compressor or pump with fluid injection to influence the boundary layer Expired - Fee Related EP2226509B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10355241A DE10355241A1 (en) 2003-11-26 2003-11-26 Fluid flow machine with fluid supply
EP04024292A EP1536147B1 (en) 2003-11-26 2004-10-12 Turbo compressor or pump with fluid injection to influence the boundary layer

Related Parent Applications (1)

Application Number Title Priority Date Filing Date
EP04024292.7 Division 2004-10-12

Publications (3)

Publication Number Publication Date
EP2226509A2 EP2226509A2 (en) 2010-09-08
EP2226509A3 true EP2226509A3 (en) 2011-06-08
EP2226509B1 EP2226509B1 (en) 2012-07-25

Family

ID=34442296

Family Applications (6)

Application Number Title Priority Date Filing Date
EP10006371A Withdrawn EP2226511A3 (en) 2003-11-26 2004-10-12 Turbo compressor or pump with fluid injection to influence the boundary layer
EP10006368.4A Expired - Fee Related EP2226510B1 (en) 2003-11-26 2004-10-12 Turbo compressor or pump with fluid injection to influence the boundary layer
EP04024292A Expired - Fee Related EP1536147B1 (en) 2003-11-26 2004-10-12 Turbo compressor or pump with fluid injection to influence the boundary layer
EP10001422A Expired - Fee Related EP2182172B1 (en) 2003-11-26 2004-10-12 Compressing turbomachine with fluid injection
EP10006367A Expired - Fee Related EP2226509B1 (en) 2003-11-26 2004-10-12 Turbo compressor or pump with fluid injection to influence the boundary layer
EP10006370A Expired - Fee Related EP2228542B1 (en) 2003-11-26 2004-10-12 Turbo compressor or pump with fluid injection to influence the boundary layer

Family Applications Before (4)

Application Number Title Priority Date Filing Date
EP10006371A Withdrawn EP2226511A3 (en) 2003-11-26 2004-10-12 Turbo compressor or pump with fluid injection to influence the boundary layer
EP10006368.4A Expired - Fee Related EP2226510B1 (en) 2003-11-26 2004-10-12 Turbo compressor or pump with fluid injection to influence the boundary layer
EP04024292A Expired - Fee Related EP1536147B1 (en) 2003-11-26 2004-10-12 Turbo compressor or pump with fluid injection to influence the boundary layer
EP10001422A Expired - Fee Related EP2182172B1 (en) 2003-11-26 2004-10-12 Compressing turbomachine with fluid injection

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP10006370A Expired - Fee Related EP2228542B1 (en) 2003-11-26 2004-10-12 Turbo compressor or pump with fluid injection to influence the boundary layer

Country Status (3)

Country Link
US (1) US7387487B2 (en)
EP (6) EP2226511A3 (en)
DE (2) DE10355241A1 (en)

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DE102008004834A1 (en) 2008-01-17 2009-07-23 Rolls-Royce Deutschland Ltd & Co Kg Radial compressor with removal and return of air at the housing
EP2083148A3 (en) * 2008-01-23 2012-06-06 Rolls-Royce Deutschland Ltd & Co KG Gas turbine with a compressor with run-in coating and method of lapping the free extremities of compressor blades in a gas turbine
DE102008009604A1 (en) 2008-02-15 2009-08-20 Rolls-Royce Deutschland Ltd & Co Kg Housing structuring for stabilizing flow in a fluid power machine
DE102008011644A1 (en) * 2008-02-28 2009-09-03 Rolls-Royce Deutschland Ltd & Co Kg Housing structuring for axial compressor in the hub area
DE102008015207A1 (en) * 2008-03-20 2009-09-24 Rolls-Royce Deutschland Ltd & Co Kg Fluid injector nozzle
DE102008031982A1 (en) * 2008-07-07 2010-01-14 Rolls-Royce Deutschland Ltd & Co Kg Turbomachine with groove at a trough of a blade end
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Also Published As

Publication number Publication date
DE10355241A1 (en) 2005-06-30
EP2226510A2 (en) 2010-09-08
EP2226511A3 (en) 2011-06-15
US7387487B2 (en) 2008-06-17
EP1536147A2 (en) 2005-06-01
EP2182172A1 (en) 2010-05-05
EP2226511A2 (en) 2010-09-08
EP2226509B1 (en) 2012-07-25
EP2228542B1 (en) 2012-05-16
US20050141990A1 (en) 2005-06-30
EP2226510B1 (en) 2013-08-28
DE502004011970D1 (en) 2011-01-20
EP2182172B1 (en) 2012-05-16
EP1536147B1 (en) 2010-12-08
EP2228542A1 (en) 2010-09-15
EP2226510A3 (en) 2011-06-15
EP1536147A3 (en) 2008-04-09
EP2226509A2 (en) 2010-09-08

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